Energy management system for propulsion of electric aircraft

Abstract

The invention discloses an energy management system for electric aircraft propulsion, which belongs to the technical field of electric aircraft energy management, and comprises an energy management unit and a high-power protection device, and the energy management unit is connected with the high-power protection device; the energy management unit comprises a control unit, a power unit and an aviation cable module; the control unit is connected with the power unit through an aviation cable module; the aviation cable module comprises a communication cable and a power cable. By means of the mode, the energy management system is suitable for different types of aviation propulsion systems, a control management system capable of being freely combined can be designed according to the high-redundancy and high-reliability requirements of the aviation systems, and the functions achieved by the control management system include but not limited to the energy management requirement under a hybrid electric propulsion scheme or a pure electric propulsion scheme.

Description

Technical Field

[0001] The present invention relates to the technical field of electric aircraft energy management, and in particular to an energy management system for electric aircraft propulsion. Background Art

[0002] As the world pays more and more attention to environmental protection and sustainable development, electric aircraft, as a new type of green transportation, is gradually becoming a research hotspot in the aviation field.

[0003] In the development of electric aircraft, high-voltage power distribution systems play a vital role.

[0004] High-voltage power distribution systems can significantly improve the transmission efficiency of electric energy and reduce line losses, thereby increasing the aircraft's range and payload; at the same time, the application of high-voltage technology enables electric aircraft to use more compact and lightweight electrical equipment, further optimizing the aircraft's overall structure and performance.

[0005] For example, in some new electric aircraft designs, a power distribution system with a voltage of 800V or even higher is used. Compared with the traditional low-voltage system, the power transmission efficiency is improved several times, effectively reducing the weight and cost of the aircraft.

[0006] Although the introduction of high-voltage power distribution systems has brought many advantages, it has also brought new challenges to the aircraft's electrical system; among them, effective control and management strategies are particularly important:

[0007] First, the stability and safety of the high-voltage power distribution system are crucial. Excessive voltage may cause serious problems such as insulation failure and arc discharge. Therefore, precise control strategies are needed to ensure the stable operation of the system under various working conditions and avoid abnormal conditions such as overvoltage and overcurrent.

[0008] Secondly, energy management strategies directly affect the endurance and flight performance of electric aircraft. Reasonable allocation and management of electrical energy and efficient use of energy are of great significance for extending the flight time of aircraft and improving flight efficiency.

[0009] Furthermore, fault diagnosis and fault-tolerant control in high-voltage power distribution systems are also important components of control and management strategies; timely and accurate detection and diagnosis of system faults and taking corresponding fault-tolerant measures can improve the reliability and availability of the system and ensure the flight safety of the aircraft.

[0010] Based on this, the present invention designs an energy management system for electric aircraft propulsion to solve the above problems. Summary of the invention

[0011] In view of the above-mentioned shortcomings of the prior art, the present invention provides an energy management system for electric aircraft propulsion.

[0012] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0013] An energy management system for electric aircraft propulsion, comprising an energy management unit and a high-power protection device, wherein the energy management unit is connected to the high-power protection device;

[0014] The energy management unit includes a control unit, a power unit and an aviation cable module;

[0015] The control unit is connected to the power unit via an aviation cable module;

[0016] The aviation cable module includes a communication cable and a power cable. The control unit is connected to the power unit through the communication cable, and the power unit is connected to the control unit through the power cable. The power unit sends voltage and current sampling data to the control unit through the communication cable, and the control unit sends control operation instructions to the power unit through the power cable.

[0017] The control unit is provided in plurality and the plurality of control units are connected by communication cables;

[0018] The power unit is provided in plurality and the plurality of power units are connected by power cables;

[0019] One control unit can control multiple power units simultaneously, and one power unit can also be controlled by multiple control units.

[0020] Furthermore, the control unit includes a current detection module for detecting current data information, a voltage detection module for detecting voltage data information, a power device control module for running a control main program, a power supply module for power supply and a communication module for information transmission; the current detection module and the voltage detection module are both communicatively connected to the power device control module, the power device control module is communicatively connected to the communication module, the power device control module is electrically connected to the power supply module, the communication cable is communicatively connected to the current detection module and the voltage detection module, and the communication module is communicatively connected to the power cable.

[0021] Furthermore, the power device control module adopts a power module to connect to an external power supply or uses a power unit to supply power through a power cable.

[0022] Furthermore, the current detection module and the voltage detection module adopt an ADC circuit; the ADC circuit includes an ADC chip and peripheral circuits, the ADC chip is used to receive the voltage, current and temperature sampling data transmitted by the power unit for analog / digital conversion, and transmit the data to the power device control module for processing, and after receiving various external signals including those returned by the ADC circuit, the power device control module outputs a control signal after logical judgment to close or disconnect the power device in the power unit and other operations.

[0023] Furthermore, the power device control module includes a control chip, an extension chip and a drive circuit; the control chip is connected to the extension chip, the main control chip and the extension chip are both connected to the drive circuit, and the drive circuit is connected to the power unit.

[0024] Furthermore, the communication module includes a communication chip and peripheral circuits, and the communication module adopts CAN communication, Ethernet communication and other aviation communication standards.

[0025] Furthermore, the high-power protection device includes a primary power device and a secondary power device, both of which are communicatively connected to the power unit, and the primary power device is communicatively connected to the power cable; the primary power device and the secondary power device are controllable devices or uncontrollable devices, and the controllable devices include contactors, IGBTs and MOSFETs, etc.; the uncontrollable devices include but are not limited to fuses, circuit breakers, solid-state fuses, solid-state circuit breakers, etc.

[0026] Furthermore, the power unit includes a power distribution module for distributing input and output electric energy, a voltage sampling module for collecting voltage data information, a current sampling module for collecting current data information, an insulation detection module for performing insulation loop resistance testing on energy input equipment or secondary electrical equipment, and a temperature detection module for collecting internal circuit temperature data information. The output end of the power distribution module is communicatively connected to the primary power device, the output end of the power distribution module is communicatively connected to the secondary power device, the secondary power device is communicatively connected to the voltage sampling module, the current sampling module, and the insulation detection module, and the voltage sampling module, the current sampling module, and the insulation detection module are all communicatively connected to the communication cable.

[0027] Furthermore, the power distribution module is a bus bar.

[0028] Furthermore, the voltage sampling module is a Hall element, the current sampling module is a high-power shunt resistor, and the insulation detection module is a temperature sensor.

[0029] Compared with the prior art, the present invention has the following beneficial effects: the key point of the present invention is that the proposed energy management system is applicable to different types of aviation propulsion systems. According to the high redundancy and high reliability requirements of aviation systems, a set of control management systems that can be freely combined is designed, and the functions it implements include but are not limited to the energy management requirements under hybrid electric propulsion or pure electric propulsion schemes. The energy management system provides a complete design solution for the high reliability design of energy management of hybrid electric aircraft and pure electric aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the prior art descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0031] Figure 1 is a block diagram of an energy management system for electric aircraft propulsion according to the present invention;

[0032] Figure 2 The connection frame of the energy management unit of the present invention Figure 1 ;

[0033] Figure 3 The connection frame of the energy management unit of the present invention Figure 2 ;

[0034] Figure 4 The connection frame of the energy management unit of the present invention Figure 3 ;

[0035] Figure 5 The connection frame of the energy management unit of the present invention Figure 4 ;

[0036] Figure 6 The connection frame of the power unit of the present invention Figure 1 ;

[0037] Figure 7 The connection frame of the power unit of the present invention Figure 2 ;

[0038] Figure 8 is a schematic block diagram of an aviation cable module of the present invention;

[0039] Fig. 9 It is a schematic block diagram of a high-power protection device of the present invention.

[0040] The numbers in the figure represent:

[0041] 1. Energy management unit; 2. High-power protection device; 11. Control unit; 12. Power unit; 13. Aviation cable module; 111. Current detection module; 112. Voltage detection module; 113. Power device control module; 114. Power module; 115. Communication module; 121. Power distribution module; 122. Voltage sampling module; 123. Current sampling module; 124. Insulation detection module; 125. Temperature detection module; 131. Communication cable; 132. Power cable; 21. Primary power device; 22. Secondary power device. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0043] Embodiment 1: In some embodiments, please refer to the drawings of the specification Figure 1 , Figure 2 and Figure 8 , an energy management system for electric aircraft propulsion, comprising an energy management unit 1 and a high-power protection device 2, wherein the energy management unit 1 is connected to the high-power protection device 2;

[0044] The main functions of the high-power protection device 2 include: selecting a suitable protection device according to the maximum voltage and current during normal operation of the circuit, and disconnecting the circuit within a specified time when abnormal conditions such as overvoltage, overcurrent, short circuit, etc. occur in the circuit to ensure the safety of aviation cables and secondary equipment. The reliability of the high-power protection device 2 must be higher than any device in the circuit to ensure system-level reliability.

[0045] The energy management unit 1 includes a control unit 11, a power unit 12 and an aviation cable module 13;

[0046] The control unit 11 is connected to the power unit 12 via an aviation cable module 13;

[0047] The aviation cable module 13 includes a communication cable 131 and a power cable 132. The control unit 11 is connected to the power unit 12 via the communication cable 131, and the power unit 12 is connected to the control unit 11 via the power cable 132; the power unit 12 sends voltage and current sampling data to the control unit 11 via the communication cable 131, and the control unit 11 sends control operation instructions to the power unit 12 via the power cable 132, thereby ensuring the normal operation of the high-voltage power distribution system.

[0048] The control unit 11 is provided with a plurality of control units 11 and the plurality of control units 11 are connected to each other via communication cables 131 ; one of the communication cables 131 is selected as a gateway to ensure that the control logics of all the control units 11 are synchronized.

[0049] The power units 12 are provided in plurality and the plurality of power units 12 are connected by power cables 132 ; the connection lines of each power unit 12 may be the same or different, and are designed according to the power distribution network.

[0050] One control unit 11 can control multiple power units 12 simultaneously, and one power unit 12 can also be controlled by multiple control units 11 .

[0051] The control unit 11 and the power unit 12 can be combined in any quantity as required, ensuring that the present invention can achieve efficient and reliable power distribution management under any channel input and output.

[0052] All circuit designs within the control unit 11 must take redundancy and scalability into consideration to ensure the reliability of the system-level design and to be adaptable to power units 12 of any design to the maximum extent possible.

[0053] When there are multiple power units 12 in the system, the power units 12 increase interconnected power devices according to demand to connect the power units 12 and improve the redundancy and reliability of the overall power grid.

[0054] The key point of the present invention is that the proposed energy management system is suitable for different types of aviation propulsion systems. According to the high redundancy and high reliability requirements of the aviation system, a control management system that can be freely combined is designed, and the functions it implements include but are not limited to the energy management requirements under hybrid electric propulsion or pure electric propulsion schemes.

[0055] The energy management device and system provide a complete design solution for the high-reliability design of energy management for hybrid-electric aircraft and pure electric aircraft.

[0056] Embodiment 2: In some embodiments, Figure 1-9 As shown, as a preferred embodiment of the present invention, Figure 3 , Figure 4 and Figure 5As shown, the control unit 11 includes a current detection module 111 for detecting current data information, a voltage detection module 112 for detecting voltage data information, a power device control module 113 for running a control main program, a power supply module 114 for power supply and a communication module 115 for information transmission; the current detection module 111 and the voltage detection module 112 are both communicatively connected to the power device control module 113, the power device control module 113 is communicatively connected to the communication module 115, the power device control module 113 is electrically connected to the power supply module 114, the communication cable 131 is communicatively connected to the current detection module 111 and the voltage detection module 112, and the communication module 115 is communicatively connected to the power cable 132.

[0057] The power device control module 113 is powered by an external power supply connected to the power module 114 or by the power unit 12 through a power cable 132 .

[0058] The current detection module 111 and the voltage detection module 112 use an ADC circuit; the ADC circuit includes an ADC chip and a peripheral circuit. The ADC chip is used to receive the voltage, current and temperature sampling data transmitted by the power unit 12 for analog / digital conversion, and transmit the data to the power device control module 113 for processing. After receiving various external signals including those returned by the ADC circuit, the power device control module 113 outputs a control signal after logical judgment to close or disconnect the power device in the power unit 12.

[0059] The power device control module 113 includes a control chip, an extension chip and a drive circuit; the control chip is connected to the extension chip, the main control chip and the extension chip are both connected to the drive circuit, and the drive circuit is connected to the power unit 12 .

[0060] The driving circuit is controlled by a main control chip and an extended control chip, and is divided into driving circuits of different power levels. The extended chip serves as a backup or signal expansion of the main control chip, which can ensure that when the number of output control signals of the main control chip cannot meet the control requirements, the extended chip can provide additional control signals, and can also serve as a redundant backup of the main control chip to ensure the high reliability of the control unit 11.

[0061] The power supply module 114 is used to convert the external power supply into the power supply voltage of the control chip; it should be noted that the power supply module 114 needs to consider the situation of multi-channel redundant power supply.

[0062] The communication module 115 includes a communication chip and a peripheral circuit. The communication circuit selects a specific communication chip and a peripheral circuit according to design requirements. The communication module 115 adopts CAN communication, Ethernet communication and other aviation communication standards.

[0063] like Figure 6 , Figure 7 and Fig. 9 As shown, the high-power protection device 2 includes a primary power device 21 and a secondary power device 22. The primary power device 21 and the secondary power device 22 are both communicatively connected to the power unit 12, and the primary power device 21 is communicatively connected to the power cable 132; the primary power device 21 is used for inputting electric energy, and the secondary power device 22 is used for outputting electric energy; the primary power device 21 and the secondary power device 22 are controllable devices or uncontrollable devices, and the controllable devices include contactors, IGBTs, MOSFETs, etc.; the uncontrollable devices include but are not limited to fuses, circuit breakers, solid-state fuses, solid-state circuit breakers, etc.

[0064] like Figure 6 and Figure 7 As shown, the power unit 12 includes a power distribution module 121 for distributing input and output electric energy, a voltage sampling module 122 for collecting voltage data information, a current sampling module 123 for collecting current data information, an insulation detection module 124 for performing insulation loop resistance testing on energy input equipment or secondary electrical equipment, and a temperature detection module 125 for collecting internal circuit temperature data information. The output end of the power distribution module 121 is communicatively connected to the primary power device 21, the output end of the power distribution module 121 is communicatively connected to the secondary power device 22, the secondary power device 22 is communicatively connected to the voltage sampling module 122, the current sampling module 123, and the insulation detection module 124, and the voltage sampling module 122, the current sampling module 123, and the insulation detection module 124 are all communicatively connected to the communication cable 131.

[0065] The power distribution module 121 is a bus bar.

[0066] The voltage sampling module 122 is a Hall element, the current sampling module 123 is a high-power shunt resistor, and the insulation detection module 124 is a temperature sensor.

[0067] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements will not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An energy management system for electric aircraft propulsion, characterized in that: It comprises an energy management unit (1) and a high-power protection device (2), wherein the energy management unit (1) is connected to the high-power protection device (2); The energy management unit (1) comprises a control unit (11), a power unit (12) and an aviation cable module (13); The control unit (11) is connected to the power unit (12) via an aviation cable module (13); The aviation cable module (13) comprises a communication cable (131) and a power cable (132); the control unit (11) is connected to the power unit (12) via the communication cable (131), and the power unit (12) is connected to the control unit (11) via the power cable (132); the power unit (12) sends voltage and current sampling data to the control unit (11) via the communication cable (131), and the control unit (11) sends control operation instructions to the power unit (12) via the power cable (132); The control unit (11) is provided in plurality and the plurality of control units (11) are connected via a communication cable (131); The power unit (12) is provided in plurality, and the plurality of power units (12) are connected via power cables (132); One control unit (11) can control a plurality of power units (12) simultaneously, and one power unit (12) can also be controlled by a plurality of control units (11).

2. The energy management system for electric aircraft propulsion according to claim 1, characterized in that: The control unit (11) comprises a current detection module (111) for detecting current data information, a voltage detection module (112) for detecting voltage data information, a power device control module (113) for running a control main program, a power supply module (114) for power supply, and a communication module (115) for information transmission; the current detection module (111) and the voltage detection module (112) are both communicatively connected to the power device control module (113), the power device control module (113) is communicatively connected to the communication module (115), the power device control module (113) is electrically connected to the power supply module (114), the communication cable (131) is communicatively connected to the current detection module (111) and the voltage detection module (112), and the communication module (115) is communicatively connected to the power cable (132).

3. The energy management system for electric aircraft propulsion according to claim 2, characterized in that: The power device control module (113) uses a power module (114) to connect to an external power source for power supply or uses a power unit (12) to supply power through a power cable (132).

4. The energy management system for electric aircraft propulsion according to claim 3, characterized in that: The current detection module (111) and the voltage detection module (112) use an ADC circuit; the ADC circuit comprises an ADC chip and a peripheral circuit; the ADC chip is used to receive voltage, current and temperature sampling data transmitted by the power unit (12) to perform analog / digital conversion, and transmit the data to the power device control module (113) for processing; after receiving various external signals including those returned by the ADC circuit, the power device control module (113) outputs a control signal through logical judgment to close or open the power device in the power unit (12).

5. The energy management system for electric aircraft propulsion according to claim 4, characterized in that: The power device control module (113) comprises a control chip, an extension chip and a drive circuit; the control chip is connected to the extension chip, the main control chip and the extension chip are both connected to the drive circuit, and the drive circuit is connected to the power unit (12).

6. The energy management system for electric aircraft propulsion according to claim 5, characterized in that: The communication module (115) comprises a communication chip and a peripheral circuit, and the communication module (115) adopts CAN communication, Ethernet communication and other aviation communication standards.

7. The energy management system for electric aircraft propulsion according to claim 6, characterized in that: The high-power protection device (2) comprises a primary power device (21) and a secondary power device (22), the primary power device (21) and the secondary power device (22) are both communicatively connected to the power unit (12), and the primary power device (21) is communicatively connected to the power cable (132); The primary power device (21) and the secondary power device (22) are controllable devices or uncontrollable devices. The controllable devices include contactors, IGBTs and MOSFETs; the uncontrollable devices include fuses, circuit breakers, solid-state fuses and solid-state circuit breakers.

8. The energy management system for electric aircraft propulsion according to claim 7, characterized in that: The power unit (12) comprises a power distribution module (121) for distributing input and output electric energy, a voltage sampling module (122) for collecting voltage data information, a current sampling module (123) for collecting current data information, an insulation detection module (124) for performing insulation loop resistance testing on energy input equipment or secondary electrical equipment, and a temperature detection module (125) for collecting internal circuit temperature data information. The output end of the power distribution module (121) is communicatively connected to the primary power device (21), the output end of the power distribution module (121) is communicatively connected to the secondary power device (22), the secondary power device (22) is communicatively connected to the voltage sampling module (122), the current sampling module (123), and the insulation detection module (124), and the voltage sampling module (122), the current sampling module (123), and the insulation detection module (124) are communicatively connected to the communication cable (131).

9. The energy management system for electric aircraft propulsion according to claim 8, characterized in that: The power distribution module (121) is a bus bar.

10. The energy management system for electric aircraft propulsion according to claim 9, characterized in that: The voltage sampling module (122) is a Hall element, the current sampling module (123) is a high-power shunt resistor, and the insulation detection module (124) is a temperature sensor.

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